Inflatable cable-support apparatus for aircraft landing means



0d 17, 1950 1 R. s. cgLLEY 2,526,541

INF'L BLE CABLE- UPPORT APPARATUS R AIRCRAFT LANDING MEANS Filed Jan. 22, 1949 Patented ct. 1K7, 195,0

INFLATABLE CABLE-SUPPORT APPARATUS FOR AIRCRAFT LANDING MEANS Russell S. Colley, Cuyahoga Falls, Ohio, assignor to The B. F. Goodrich Company, New York, N. Y., a corporation of New York Application January 22, 1949, Serial No. 72,104

1.1 Claims. (01.,244-110) The invention relates to yieldable support apf cable and the like of aircraft landing or deacceleration means for stopping the aircraft on a runway or surface of limited length.

The iiight or landing deck of a warship of the aircraft carrier type presents a runway or landing surface of relatively limited extent, especially in length, as compared to that generally available at aircraft landing fields on land. For successful operation of military aircraft of the heavier-than-air type to and from the carrier ship, it has been found necessary to provide means for rapidly yet gradually de-accelerating the translational or ambulatory movement of the aircraft, once the latter has landed on the flight deck, so as to safely stop the aircraft within the length of the runway. To this end in a known, practical embodiment of aircraft de-acceleration means, there is utilized a series of longitudinally or fore-and-aft spaced-apart flexible arresting cables extending laterally or from starboard to port of the night deck across the width of the runway. The cables when in positionV for engaging a dependent landing hook of the aircraft and for stopping the aircraft, are supportedin a tensioned condition `in spaced-apart relation to the flight deck, the supports being rigid, steel support frames hingedly attached to the flight deck at laterally spaced-apart positions to the respective sides of the fore-and-aft centerlineor axis of the runway and positioned upright during landing operations.

The rigid support frames despite their retractability, constitute a safety hazard to the aircraft making a landing. For example, the direction of movement of the approaching aircraft making a landing may be angularly sidewise to the fore-and-aft axis of the runway in which case the rearwardly disposed landing hook engages off-center tending to cause yawing of the aircraft such that a landing wheel strikes the rigid support frames, whereupon the aircraft is abruptly and substantially instantaneously stopped. This frequently breaks the support frames and also produces undue stresses and severe damage to the aircraft, especiallyl since the hook and its attachment apparatus is likely to be torn loose and wholly separated from the aircraft.

Also, when the direction of movement of the approaching aircraft is, for example, parallel with the fore-and-aft axis of the runway but-the aircraft is substantially offset to a side of such axis, it is possible for a landing Wheel of the aircraft to strike directly one or more of the rigid support frames. In this case, not only the support frame or frames, the wheel, and the landing gear are damaged; but in addition, the aircraft is stopped so abruptly as to likely induce nosingover or tilting of the aircraft onto the front end Yor nose of the fuselage, which tilting may result in injury to the pilot and/or fire breaking out and consuming the aircraft, as well as probably making a major part of the de-accelerating means temporarily inoperative for subsequent aircraft landings.

An object of the invention is to overcome effectively the foregoing and other disadvantages of the aircraft de-accelerating means including the cable-support frames thereof.

Other objects of the invention are to provide for yieldably supporting and maintaining a flexible cable and the like in spaced-apart relation to a support surface; to provide means or apparatus for inflatably supporting the cable in the aforesaid relation while withstanding normal loads of the cable under tension conditions; to provide for relative movement in a plurality of directions between the cable Vand the inflatable means; to provide for substantial reduction of height of the inatable support means under impact and/or emergency overload conditions; to provide for resisting failure and wear of an inflatable element of said means despite the aforesaid relative movement; to provide for resumption of position by the cable after movement of the same from its normal spaced-apart relationship; to provide for simplicity of construction, convenience `of manufacture, installation and servicing, and for effectiveness of operation. l

Further and more specific objects are to provide an improved support means for the arresting cables of aircraft de-acceleration means; to provide for inflatably maintaining the cables in position for landing operation of aircraft; to provide for mounting and protecting an inflatable element of saidymeans on a runway surface; to provide for extensive movement of the cable relative to the inflatable element without objectionable wear of either the cable, or'the element, or

both.

These and other .objects and advantages of the invention will. be apparent from the following description.

In the accompanying drawings which form a part of this specification and in which like numerals are employed to designate like parts throughout the same,

Fig. 1 is a perspective view from above of inatable support apparatus or assemblies maintainingtensioned arresting cables of aircraft deacceleration means in spaced-apart relation to a runway surface of an aircraft carrier, parts being broken away;

Fig. 2 is a view taken along line 2-2 of Fig. 1 showing one of the inflatable support assemblies 3 and its associated cable, parts being in section and broken away;

Fig. 3 is a sectional view on an enlarged scale taken along line 3-3 of Fig. 2, parts being broken away; and

Fig. 4 is a plan view of an attaching structure or frame for mounting the apparatus on the runway surface, parts being broken away.

In the illustrative embodiment of the invention shown in the drawings, vthe construction'inchicles a yieldable support apparatus or assembly Il) adapted to normally maintain an arresting cable, rope, wire, chain, or other exible member l5 of vehicle, especially aircraft, de-acceleration means II (shown only in part) in overlying, spaced-apart relation to 'a support surface I2 such,' for examplejas the flight or landing deck of'an `aircraft carrier warship I3, which deck constitutes a runway I4. The cable I5 is normally maintained under tension by de-acceleration means l I and the cable normally extends directly acrossthe support surface I2 in the direction laterally of the translational or ambulatory movemerit of the vehicle, the direction of translational movement for illustrative purposes only being indicated by an arrow at I6. The arrangement facilitates engagement of the cable or flexible member I5 with the vehicle such, for example, as an aircraft (not shown) for gradually and rapidly stopping the translational movement of the aircraft along the supportv surface upon operation ofthe means I I.

The support assembly Il] includes extensible means 20 which Vcomprises desirably inatable means for yieldablysupporting the cable I5 in the aforesaidVspaced-apart relationship to the flight deck I2. The infiatable means 2 for the -arrangement shown in the drawings comprises an inatable tubular body of resilient rubber or other rubber-like material, reinforced or unreinforced as desired, and having a wall thickness of sufcient strength to withstand normal inating pressures which, for example, may be in the range of 31/2 to 5 pounds persquare inch. v'The tubular body in its inflated condition may have, for example, a maximum diameter of about 5 to 8 inches.

rThe inflatable tubular body 2D has desirably relatively flat, closed end portions 2l, 22 and a generally rounded or bowed contour intermediate the end portions 21,22 in the longitudinal direction'of the body for the inflated condition, as shown especially in Fig. 2 The configuration of the elongated tubular body facilitates the provision of a generally wedge-like form at each side of the transverse, vertical center-plane of the body, i.`e., its region of maximum diameter, whereby oppositely inclinedupper surfaces of the body are provided. The inclined surfaces each diverge upwardly toward one another and away from an end portion 2l, 22. The construction and arrangement facilitates sliding movement of the cable I5 in the direction of the translational movement of the aircraft, when the cable I5 is flexed from and especially when the same is being returnedk to its normal position which is shown especially in Fig. 2. The construction and arrangement is also advantageous in that, the body 2B may be positioned at either side of the runwayfld, which avoids special right and lefthand constructions. A further advantage is that the saine body 2B may be utilized-for permitting fiexure of the cable I5 in either direction longitudinally of the runway I4.

The inatable tubular body 2G intermediate its 4 ends is provided with a suitable iniiating valve 23 incommunication with the interior ofthe body 20. The end portions 2|, 22 may be vulcanized and bonded to a fully closed condition. However, portions 2Ia and 2lb of the closed end portion 2I are preferably adhesively united as by an aircuring rubber-cement so as to permit separation of the portions 2Ia, 2Ib in response to a sudden, extensive increase in the internal pressure of the inflated body to facilitate the escape of the inflating medium or air, thereby rapidly deflating the body 2!A under emergency overload conditions.

Sincev the tubular'body 20 is desirably positioned with its longitudinal axis substantially parallel with the longitudinal centerline of the runway I4 and in attached relation to the support` surface I2 and in underlying relation to the cable I5 at a position intermediate opposite margins of the runway, the sliding movement of the cable I5 under iiexure conditions, especially during lthe return thereof to the normal position, will tend to abrade the relatively soft rubber of the body 20. Accordingly, at the upper surface of the body Z, there is provided yieldable, protective means 211 adapted to resist undue wear and/or failure of the rubber wall of the body 20.

The protective means 24 may be a relatively thick sheet of suitable resilient, rubber-like material having age-resisting and wear-resisting characteristics and may include a reinforcement 25 of woven fabric, sheet material ofA cotton, linen, rayon` or other suitablermaterial'. The rubberlike, sheet material 24 and its reinforcement 25 extends substantially from one side of the tubular body to the other side thereof in overlying7 bonded relationrto the upper portion of said body 20 for presenting a bearing surface of flexible, wear-resisting characteristics to the cable I5. Reinforcing tapes 2E, 2'! of suitablerubber-like material may extend along the side margins of theuprotective means 24 in overlapping, attached relation thereto, as shown` especially in Figs. 2 and 3.

Tofacilitate freedom of slidingmovement of the cableand t0y avoid undue wear and abrasion ofthe inflatable body 2G including the means 24, theinvent-ion providesarsecond, yieldable, protective Ameans comprising a protective element 28 ofv resilient, wear-resisting material, preferably metal strip material such, for,Y example, as spring steel, disposed along and longitudinally of the body 204m relatively movable,A overlying and substantially-conforming relation therewithfor disposition betweenthe body 20 and the cable I 5.

The protective element 28'presents at its outer facel a bearing surface 2&3 extending along the element in substantial conformance to the aforesaidibowed contour of the inflatable bodyv for disposition;` laterally of the cable IE to permit the desired sliding movement ofthe cable along the bearingpsurface. The bearing surface 29 is continuous andits b owed'contour facilitates the sliding movement ofthe cable to and from the normal positionunder-exure of the cable in either direction longitudinally of theY inflatable body.

The arrangement makes possible relatively free movement of the Cable I5 along the relatively hard, smoothbearing surface 29; inasmuch as the cable rests directly upon the bearing surface 29, although under conditions of unusual flexure the cable may also contactV the other protective` meansV 2&3.k A.further advantageof the resilient protective element 28 is that it may be deformed to a ,relatively flattened configuration of reduced height under accidentalfimpaot' thereon 'byfthe aircraft, thereby foffe'ring minimum resistance t0 the'passage ofthe aircraft thereover.`

' Iheinvention provides frame ,means 36 for mounting the inflatablel tubularbody 2 8 'on the i flight deck VI2 and desirably for retaining the protective element 28 in its longitudinally, over-` and an attaching element 32, each of suitablel metal strip material.

` The T-shaped element 3| has an attaching portion 33 disposed at right angles to the leg portion constituting the protective element 28 which may be integrally united with the attaching'portion 33. The attaching portion 33 is c entrally offset to accommodate the flattened end portion 22 of the inflatable' body '20 intermediate apertured ends 36, 36 of the portion 33 for facilitating securely clamping the endportion 22 between the element 3| and the flight deck |72. YThe leg portion 28 for the assembled conditionextends desirably beyond the attaching element 32 which is disposed at the opposite end portion 2| ofthe inflatable body.

The attaching element 32, like the attaching portion 33, is centrally offset for receiving the end portion 2|, clamping the latter securely in place, as shown; especially in Fig. 3. The element'32 at the immediate central area thereof has a recessed vportion 34 to accommodate the protective element 28 so as to permit relative movement of the protectivev element 28 with respect to the attaching element 32 under substantial flattening of the protective element28 by accidental impact thereon. The element`32 hasapertured ends 35, 35 for receiving screw fasteners 38, 38 or other suitable fastening means for securing the frame means to the flight deck, as shown especially in Figs. 1, 2 and 3. v y

' VIn attaching the"v apparatus II] Ito the flight deck I2,V the inflatable tubular body 28 in the deilated condition is disposed upon the flight deck with the; longitudinal axis ofthe body substantially parallel to the longitudinal aXis of the runway I4 andv at. the desired location to one side of such axis of the runway intermediate the ends ofthe arresting cable l5, as shown especially in Fig. 1.' The tubular body 20 need not be adhered to the flight deck I2. The frame means 3|! may then be positioned with the attaching portion 33 of the T-shaped element 3| in the desired overlapping and clamping relation to the flat end portion 22 and with the protective element 28 extending along the longitudinal axis of the inflatable body in overlying relation therewith and beneath the cable I5. The attaching element 32 may then be disposed in overlapping, clamping relation to the other flat end portion 2| with the protective element 28 extending through the recessed portion 34 in relatively moveable relation therewith. The screw fasteners 38,38' extend through the apertures in the end portions 35, 35 and 36, 36 and engage the underlying structure of the flight deck I2. g

vThe inflatable body 20 is inflated to the desired pressure by means of the valve'23 to obtain the generally bowed or double wedge-like configuration, as shown especially in Figs. 2 and The body 2|! in the inflated condition, the V'protective means 24 and the protective element 28 are in substantial conformance with the con figuration of each other longitudinally f th inflatable body and make possible yieldably supporting the cable I5 under tension in its normal position at the region of maximum height of the apparatus IU longitudinally thereof, as shown especially in Fig. 2. The cable I5 rides upon the bearing surface 29 of the protective element 28 and is free to slide longitudinally of Athe body 20 in either direction thereof under Ilexure of the cable upon engagement of the latter withthe aircraft. The apparatus Ill under accidental impact as by the landing wheel of the aircraft, is capable of being reduced in height to a relatively flat configuration and the inflatable body is adapted to be deflated by the separation of the portions 2 Ia and 2 Ib of the end portion 2 I, whereby the apparatus I0 offers minimum resistance to the passage of the aircraft thereover.

A second apparatus I0 is mounted in a like manner at the opposite margin and corresponding location of the runway |4, as shown especially in Fig. 1, so that the cable l5 in its tens'ioned condition is supported in substantially parallel spaced-apart relation to the flight deck between the pair of apparatus I0, I0, the respective ends of the cable I5 being connected in a suitable manner to the aircraft de-acceleration means which is largely concealed below the eight deck l2.

For landing aircraft a plurality of the laterallyextending cables I5, I5 may be positioned spacedaparty Iin series longitudinally of the runway throughout the extent of the desired landing area. Each cable I5 is supported yieldably by a pair of the inflatable apparatus I8, I0 constructed and arranged as described hereinabove. In 'the landing operation any one of thev cables may be engaged by the dependent landing hook of the aircraft, whichengaged cable thereupon'is flexed in the direction longitudinally of the runway such, for example, as'indicated by the arrow |6. Under flexure the cable I5 may slide at least part way along the bearing surfaces 29, 29 of the protective elements 28, 28 while the aircraft de-acceleration means |I functions to grad` ually yet rapidly stop the translational movement of the aircraft. Upon stopping the aircraft, the cable I5 is disengaged from the latter and returned to its normal position upon the apparatus I, I0 by sliding on and along the bearing surface 29 until the cable again extends directly Vacross the landing runway.

When the aircraft is traveling in an 'angularly sidewise direction to the longitudinal axis of the runway, the reaction of the flexed cable may cause the aircraft to swing around such that its landing wheel contacts one or more of the apparatus I0, whereupon the protective element 28 is flattened to a lower height and the inflatable body 2U rapidly deflates under the impact, thus advantageously permitting relatively free movement of the aircraft over the'apparatus I0 In case the aircraft is landing substantially parallel to the longitudinal axis of the runway I4 but to one side thereof, the landing wheel may strike one or more of the apparatus I0, whereupon the apparatus assumes a relatively flat configuration of reduced height for offering minimum resistance to the passage of the landing wheel thereover. This avoids nosing-over or other damage to the aircraft, while assuring the safety of the pilot of the aircraft.

Variations may be made Without departing from the scope of the invention 'as it is defined in the following claims.

lfclaim: l n 1. Apparatus ,fonv normally maintainingY an arresting cable andthe like of vehicle cie-accelera.- tion meansrinf overlying spaced-apart relation to asupport surface to facilitate engagement of said cable with the vehicle for gradually and rapidly stopping translational movement of said vehicle along said surface by virtue of operationl of said means, said apparatus comprising extensible means for yieldably supporting said cable in the spaced-apart relationship, whichy cable under tension normally extends directly across the Support surface in the direction laterally of saidY movement of the vehicle, said extensible means being positionable at the support surface in attached relation thereto and in underlying relation to said cable at a position intermediate opposite margins of the support surface, and yieldable protective means including a bearing surface of flexible wear-resisting material in operative overlying association with said extensible means for presenting said bearing surface to saidr cable, said protective means being constructed and arranged for permitting sliding movement of said cable along said bearing surface in the direction of; said translational movement under flexure of said cable from its normal position upon said engagement thereof with the vehicle and for contacting at said bearing surface said cable in the normal and flexed conditions thereof, said extensible means and said protective means being deformable to a configuration of relatively reduced height under accidental impact thereon by thelvvehicle for offering minimum resistance to the movemnt of the Vehicle thereover.

2. Apparatus for normally maintaining an arresting cable and the like of aircraft de-accelerationv means in overlying spaced-apart relation to a support surface to facilitate engagement of said cable with the aircraft for gradually and rapidly stopping translational movement of said aircraft along said surface by virtue of operation of said means', said apparatus comprising extensible means for yieldably supporting said cable in the spaced-apart relationship, which cable under tension normally extends directly across the support surface in the direction laterally of said movement ofthe aircraft, said extensible means beingl positionable at the support surface in attached relation thereto and in underlying relation to said cable at a position intermediate opposite margins of the support surface, and a protective element of flexible Wear-resisting material in operative overlying association with said extensible means for disposition between the latter means and said cable, said protective element presenting a bearing surface of said Wear-resisting material extending along said element for disposition laterally of said cable and being constructed and arranged to permit sliding movement of said cable along said bearing surface in the direction of said translational movement under flexure of said cable from its normal position upon said engagement thereof with the aircraft and to contact at vsaid bearing surface said cable in the normal and flexed conditions thereof, said extensible means and said protective element being deformable to a configuration of relatively reduced height under accidental impact thereon by the aircraft for 'offering minimum resistance to the translational movement of the aircraft thereover.

3. Apparatus for normally maintaining an arresting cable and the like of aircraft de-acceleration means in overlying spaced-apart relation to .a support surface to facilitate engagement 0f said lil) 8 cablewith thel aircraft for graduallyand rapidly stopping translational movementof said aircraft along said surface by virtue of operation of saidY m-eans, said apparatus comprising inflatable means for yieldably supporting said cable in the spaced-apart relationship, which cable under tension normally extends directly across the support surface in thel direction laterally of said movement of the aircraft, said inflatable means being positionable at the support surface in attached relation thereto and in underlying relation to said cable. at a -position intermediate opposite margins ofthe support surface, and yieldable protective means including a bearing surface of flexible wear-resisting material in operative overlying association with said inflatable means for presenting said bearing surface to said cable, said protective means being constructed and arranged for permitting sliding movement of said cable along said bearing surface in the direction of said translational movement under flexure of said cable from its normal position upon said engagement thereof with the aircraft and for contacting at said bearing surface said cable in the normal and flexed conditions thereof, said inflatable means and said protective means being deformable to a configuration of relatively reduced height under accidental impact thereon by the aircraft for offering minimum resistance to the movement of the aircraft thereover.

4. Apparatus for normally maintaining an arresting cable and the like of aircraft de-acc-eleration means in overlying spaced-apart relation to a support surface to facilitate engagement of said cable with the aircraft for gradually and rapidly stopping translational movement of said aircraft along said surface by virtue of operation of said means, said apparatus comprising inflatable means for yieldably supportingk said cable in the spaced-apart relationship, which cable under tension normally extends directly across the support surface in the direction laterally of said movement of the aircraft, said inflatable means being, positionable at the support surface in attached relation thereto and in underlying relation to said cable at a position intermediate opposite margins of the support surface, and a` protectiveelement of flexible wear-resisting material in operative overlying association with said inatable means for disposition between the latter means and said cable, said protective element presenting a bearing surface of said Wear-resisting material extending along said element for disposition laterally of said cable and being constructed and arranged to permit sliding movement of said cable along said bearing surface in the direction of said translational movement under flexure of said cable from' its normal position upon said engagement thereof with the aircraft and to contact at said bearing surface said cable in the normal and flexed conditions thereof, said inflatable means and said protective element being deformable to a configuration of relatively reduced height' und-er accidental impact thereon by the aircraft for offering minimum resistance to the translational movement of the aircraft thereover.

5. Apparatus for normally maintaining an arresting cable and the like of aircraft de-acceleration means in overlying spaced-apart relation to a support surface to facilitate engagement of said cable with the aircraft for gradually and rapidly stopping translational movement of said aircraft along said surface by virtue of operation of said means, said apparatus comprising an inflatable closed hollow body of generallyl Wedge-like contoury ina direction thereof viti-the a inflated conditionv and positionable at the supportsurface in attached relation thereto and .in underlying relation to said cable at a position intermediate opposite margins of the support surface for yieldably supporting in said condi- Ation said cable in the spaced-apart relationship, which cable under tensionnormally extends vdirectly, across the support surface in the direction laterally of said movement of the aircraft and of said contour of said body, and body pro- ,tective means :comprising a protective element of `Aresilient wear-resisting material extending in 1 loperative overlying association with the inflatvable body in said direction thereof for disposition between Vsaid body and said cable, said protective element presenting a bearing surface Y of said wear-resisting material extending along said element for disposition laterally of said cable, 4said element including said bearing surface having substantial conformance to the inflated contour of saidinlatable body in the direction along said bearing surface for permitting sliding movement of said cable along said bearing surface in the direction of said translational movement f' kunderl ilemre of said cable from its normal position upon said engagement thereof with the aircraft, said .inflatable body and said protective element being deformable tov a configuration' of relatively reduced height under accidental im- Y pact l'thereon by the aircraft for offering minij mum resistance to the passage of lthevaircraft thereover.

6. Apparatus for normally maintaining an arresting cable and the like of aircraft de-accelera- `r ltion means in overlying spaced-apart relation to a support surface to facilitate engagement `of Asaid cable with' the aircraft for graduall-yY and rapidly stopping translational movement of said aircraftalong said surface by virtueof opera- '.'Ition of said means, said apparatus comprising 4 an inflatable tubularbody having'closed ends and a generally rounded contour intermediate jsaid ends and longitudinallylof the body in the inflated condition, said' body being positionable 'laterally of said movement of the'aircraft, and

' body protective means comprising` a'protective y. 'element of resilient relatively hardwear-resist- 'ing material disposed longitudinally 'of the'invflata'ble body' inV operative-overlying' association therewith for vdisposition betweenvs'aid body and said cable,` said protective velement' presenting a bearing surfacey of Vsaid wear-resisting material extending longitudinally of said inilatable body in substantial conformance to said contour thereof for disposition laterally of said cablerto permit'sliding movement ofI said 'cable along said bearing surface in the directionof said' translational movement under flexure--of said cable from its normal position upon said engagement thereof. with the aircraft,A said inflatable body and saidprotective element being deformable .toarelatively flattened configuration of reduced height under accidental impact thereon 1by lthe aircraft for offering minimum resistance tothe passage of the aircraft thereover` Y '7. Apparatusfor normally maintaining an arresting cable andthe likerofaircraft de-acceleration means in overlying spaced-apart relation to a'support surface to facilitate engagement of said cable with the aircraft for gradually and rapidly vstopping translational movement of said aircraft-along said surface by virtue of operation of said means, said apparatus comsitionable in underlying relation to said lcable intermediate opposite margins of the support surfacefor yieldably supporting in said condition said cable in A the spaced-apart relationship, which `cable under tension normally extends directly across the support surface in the direction laterally of said movement of the aircraft, and

'body protective means comprising a protective element of resilient wear-resisting metal material disposed longitudinally of the inflatable bodyv inA relatively movable'overlying relation therewith for disposition between said body and said cable, said protective 'element presenting -a bearingv surface of said metal material extending along the same in substantial conformance 'to'said 'contour of saidinflatable body for disposition laterally of said cable to permit'sliding movement of said cable along said bearingsur- Vface'fin` the direction of said translational movement runder` flexure of said cable from its 'norr'mal position upon said engagementthereof rwith the aircraft, 'said' 4inflatable body'and said vprotective element being' deformable to a lrelatively l flattened configuration 'of' reduced height under accidental rimpact'thereon by the aircraft for offering minimum' resistance to the rpassa'ge of the 'aircraftthereoven 'andmeans for Yattaching f said inflatable body to said `support surface and 'for retaining said vprotective elementfin itsflonl gitudinall'y'overlying relationship tosaid'inilatable" body while permitting 'th'el accidentalfflattening of said 'protective element.

8; Apparatus for normally 'maintaining an arrestingcable-and the like of aircraftA de-acceleration means in overlying spaced-apart relation to `asupport surface to facilitate engagement of'said fcable with the aircraft for gradually and rapidly stopping translationalmovement of said aircraft alongsaid surface by' virtue of operation of said Vmeans, said apparatus comprising anV inflatable closed hollow body of generally bowed contour in a direction thereof in the inflated condition vand positionable'at' the support surface in attached relationthereto and in underlyingV relation' to said cableV at a position intermediate opposite margins of Ythe support Asurface for yieldably sup- 'l' porting l.in said 'condition said cable in the spacedapart relationship, which cable u rider tension normally extends directly acrossthe supportsurf ace in1 the direction laterallyfof said movement 'vof the aircraft and of said conteur said body,

means for ir'iilatingA said body, `means 'responsive' to an abrupt substantialincrease Vin the internal pressure of the Yinflatedbody Vfor rapidly deflating Hthe latter, and body protective means'comprising protective element'of resilient'wear-resisting material in operati'yefp'verlying vassociation with "the Iinflatable body fordi'spos'ition between the .lal'fsr .and said cable, said protective element presenting a bearing surface of said wear-resisting material extending along said element for disposition laterally of said cable, said element including said bearing surface having substantial conformance to said contour of said inflatable Vbody in the direction along said bearing `surface for permitting sliding movement of said cable along said bearing surface in the direction of said translational movement under flexure of said cable from its normal position upon said engagement thereof with the aircraft, said inatable body being deflatable and said protective element being deformable to a configuration of relatively reduced height under accidental impact thereon by the aircraft for oiering minimum resistance to the passage of the aircraft thereover.

9. Apparatus for normally maintaining an arresting cable and the like of aircraft de-acceleration means in overlying spaced-apart relation to a support surface to facilitate engagement of f vsaid cable with the aircraft for gradually and rapidly stopping translational movement of said aircraft along said surface 'by virtue of operation of said means, said apparatus comprising an inflatable tubular body having relatively flat spacedapart closed end portions and a generally bowed contour intermediate said end portions in the longitudinal direction of sa-id body in the inflated condition, one of said end portions having parts thereof adhesively united yet separable in response to an abrupt substantial increase in the internal pressure of the vinflated body for rapidly deating the latter, means for infiating said body, said body being positionable at the support surface in attached relation thereto with the longitudinal axis of the body arranged laterally of said cable and said body being Vpositionable in underlying relation to said cable intermediate opposite margins of the support surface for yieldably supporting in said condition said cable in the spaced-apart relationship, which cable under tensionnormally extends directly across the support surface in `the direction laterally of said movement of the aircraft, and body protective means comprising a `protective element of resilient wear-resisting metal material disposed longitudinally of said'body in relatively movable overlying relation therewith for disposition between said body and said cable, said protective element presenting a bearing surface of said metal material extending along the same in'substantial conformance to said contour of said inflatable body for disposition laterally of said cable to permit sliding movement of'said cable along said bearing surface in the direction of said translational movement under exure of said cable from its normal position upon said engagement thereof with the aircraft, said inflatable body being defiated and said protective element being deformable yto a relatively flattened configuration of reduced height under accidental impact thereon by the aircraft', for offering minimum resistance to the passage of the aircraft thereover, and frame means for attaching said inflatable body to said support surface and for retaining said protective element in its longitudinally overlying relationship to said inflatable Abody while permitting the accidental flattening of said protective element.

10. A frame structure attachable to a support surface for mounting thereon an infiatable tubular body having substantially at spaced-apart closed end portions. said frame structure comprising an element having an attaching portion for extending laterally of said body at one end porytion-'thereof in overlapping relation therewith and attachable to said support surface for holding said body therebetween, said element including a protective portion of resilient Wear-resisting strip metal material projecting from a side `of said attaching portion in a direction substantially normal thereto for disposition along the longitudinal axis of said body and having a conguration substantially conforming to that vof said body in the iniiated condition for positioning in overlying adjacent unattached relation to the inflated body for relative movement therebetween under bending of said protective portion, and a second element for extending laterally of said body at the other end portion thereof in overlapping relation therewith and attachable to said support surface for holding said body therebetween, said second element having a recessed portion for overlying said protective `portion in alignment therewith and accommodating the latter therethrough in slidingly movable relation therewith to permit the movement of said protective portion under bending of the same.

ll. Aircraft de-acceleration apparatus lfor gradually and rapidly stopping translational movement of the aircraft upon landing ofthe same, said apparatus comprising a support surface constituting an aircraft runway, an arresting cable of flexible material normally extending in a condition of tension directly across lsaid runway in spaced-apart relationship thereto between opposite margins thereof and 1in the direction laterally of said translational movement of the aircraft, and a pair ofyieldable vsupport assemblies each mounted on said Arunway and underlying said cable at a position adjacent and spaced-apart from one of said margins to maintain said cable in said spaced-apart relationship to the runway, each assembly comprising inflatable means disposed `on said runway for yieldably supporting said cable, and lyieldable protective means attaching said inflatable means to said runway and including a protective element of flexible wear-resisting material in operative overlying association with said inflatable Imeans and disposed between the latter and said cable, said element presenting a bearing surface :of said wear-resisting material extending laterally of said cable and constructed and arranged to permit sliding movement of said cable valong said bearing surface in the direction of said translational movement of the aircraft under ilexure of said cable from its normal position upon engagement of the aircraft with said cable and to contact said cable in the normal and flexed conditions thereof, said inflatable means and said protective element being deformable to a configuration of relatively reduced height under accidental impact thereon by the aircraft for offering minimum resistance to the passage of the aircraft thereover, and means Vfor attaching said protective means to said runway.

RUSSELL S. COLLEY.

REFERENCES CIT-ED The following references are of record in the file of this patent:

UNITED STATES PATENTS iSarcllel? May 8, 1945 

